EP2540868B1 - Splitterbeständige abreibbare turbinenluftdichtung - Google Patents

Splitterbeständige abreibbare turbinenluftdichtung Download PDF

Info

Publication number
EP2540868B1
EP2540868B1 EP12173070.9A EP12173070A EP2540868B1 EP 2540868 B1 EP2540868 B1 EP 2540868B1 EP 12173070 A EP12173070 A EP 12173070A EP 2540868 B1 EP2540868 B1 EP 2540868B1
Authority
EP
European Patent Office
Prior art keywords
layer
abrasive
coating
rotor shaft
mils
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP12173070.9A
Other languages
English (en)
French (fr)
Other versions
EP2540868A1 (de
Inventor
Christopher W. Strock
Paul W. Baumann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2540868A1 publication Critical patent/EP2540868A1/de
Application granted granted Critical
Publication of EP2540868B1 publication Critical patent/EP2540868B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/324—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal matrix material layer comprising a mixture of at least two metals or metal phases or a metal-matrix material with hard embedded particles, e.g. WC-Me
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/347—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with layers adapted for cutting tools or wear applications
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Gas turbine engines include compressor rotors with a plurality of rotating compressor blades. Minimizing the leakage of air between tips of the compressor blades and a casing of the gas turbine engine increases the efficiency of the gas turbine engine as the leakage of air over the tips of the compressor blades can cause aerodynamic efficiency losses. To minimize leakage, the gap at tips of the compressor blades is set so small that at certain conditions, the blade tips may rub against and engage an abradable seal on the casing of the gas turbine. The abradability of the seal material prevents damage to the blades while the seal material itself wears to generate an optimized mating surface and thus reduce the leakage of air.
  • Cantilevered vanes that seal against a rotor shaft are also used for elimination of the air leakage in turbine engines.
  • Current cantilevered vane tip sealing requires that the tip gaps need to be set more open than desired in order to prevent rub interactions that can cause rotor shaft spallation, vane damage or rotor shaft burn through caused by thermal runaway events during rubs.
  • Current materials have been shown to lack the durability to prevent spallation and they lack the abradability to prevent vane damage.
  • US 2003/0126800 discloses an abrasive coating which is formed by co-depositing hard particles within a matrix material onto a substrate using a cold spray process.
  • the abrasive coating of this disclosure falls outside of the scope of the present claims.
  • EP 2481890 discloses an abrasive coating forming a sealing material on components of gas turbine engines.
  • the coating of this disclosure may be found on the surface of the rotor to form a seal with the stator vanes and/or the inside of the casing to form a seal with the rotor blades.
  • the abrasive coating of this disclosure preferably contains ceramic particles in a composite matrix of hexagonal boron nitride in nickel, cobalt, copper, iron or mixtures thereof.
  • US 2010/0284797 discloses an abradable coating that comprises a band coating and a multilayer coating thereon.
  • the abradable coating of this disclosure falls outside the scope of the present claims
  • US2004/0142196 discloses an abradable seal for gas turbine engines that comprises a metal matrix and solid lubricant; hBN distributed homogeneously through the coating.
  • EP 1229252 discloses an abradable coating made of an Al-based metal matrix and a solid lubricant that canbe hBN.
  • the present invention provides an abrasive coating for a rotor shaft, the abrasive coating comprising: a metal bond coat layer on the rotor shaft; an abrasive layer over the bond layer for contact with vanes during operation of the rotor shaft, the abrasive layer including a matrix containing a filler which is of lower strength than the matrix, the filler having an increased concentration radially outward from the bond layer to the outer surface of the abrasive layer; wherein the abrasive layer contains hexagonal boron nitride (hBN) as the low strength filler in an amount that ranges from 5% to 80 %, based on the volume of the coating, the abrasive layer having an increased concentration of hBN radially outward from the bond layer to the outer surface of the abrasive layer; and wherein the matrix includes yttria stabilized zirconia or gadolinia-zirconate, or wherein the matrix includes at least one metal selected from the
  • the present invention is an abrasive coating that comprises a low strength, abrasive composite top layer on a bond coat.
  • the top layer contains an increasing amount of low strength filler in the radial direction of the coating to provide a graded cohesive strength coating so that wear or failure due to rubbing occurs at the surface of the coating.
  • the cohesive strength of the top layer may decrease from about 2,000 psi (14 MPa) at the junction with the bond coat layer to about 200 psi (1.4 MPa) at its surface.
  • the top layer may be produced by thermal spray of the ceramic particles.
  • hBN hexagonal boron nitride
  • a base bond coat may be MCr, MCrAl, MCrAlY or a refractory modified MCrAlY, where M is nickel, cobalt, iron or mixtures thereof.
  • the coating may also include an intermediate layer between the abrasive composite top layer and the bond coat.
  • the intermediate layer comprises a ceramic layer that acts as a thermal barrier to protect the rotor shaft. Ceramic layers include zirconia, hafnia, mullite, and alumina. The intermediate layer also has higher shear strength than the top coating.
  • FIG. 1 is a cross-sectional view of gas turbine engine 10, in a turbofan embodiment.
  • turbine engine 10 comprises fan 12 positioned in bypass duct 14, with bypass duct 14 oriented about a turbine core comprising compressor (compressor section) 16, combustor (or combustors) 18 and turbine (turbine section) 20, arranged in flow series with upstream inlet 22 and downstream exhaust 24.
  • compressor compressor section
  • combustor or combustors
  • Compressor 16 comprises stages of compressor vanes 26 and blades 28 arranged in low pressure compressor (LPC) section 30 and high pressure compressor (HPC) section 32.
  • Turbine 20 comprises stages of turbine vanes 34 and turbine blades 36 arranged in high pressure turbine (HPT) section 38 and low pressure turbine (LPT) section 40.
  • HPT section 38 is coupled to HPC section 32 via HPT shaft 50, forming the high pressure spool or high spool.
  • LPT section 40 is coupled to LPC section 30 and fan 12 via LPT shaft 44, forming the low pressure spool or low spool.
  • HPT shaft 42 and LPT shaft 44 are typically coaxially mounted, with the high and low spools independently rotating about turbine axis (centerline) C L .
  • Fan 12 comprises a number of fan airfoils circumferentially arranged around a fan disk or other rotating member, which is coupled (directly or indirectly) to LPC section 30 and driven by LPT shaft 44.
  • fan 12 is coupled to the fan spool via geared fan drive mechanism 46, providing independent fan speed control.
  • fan 12 is forward-mounted and provides thrust by accelerating flow downstream through bypass duct 14, for example in a high-bypass configuration suitable for commercial and regional jet aircraft operations.
  • fan 12 is an unducted fan or propeller assembly, in either a forward or aft-mounted configuration.
  • turbine engine 10 comprises any of a high-bypass turbofan, a low-bypass turbofan or a turboprop engine, and the number of spools and the shaft configurations may vary.
  • incoming airflow F I enters inlet 22 and divides into core flow F C and bypass flow F B , downstream of fan 12.
  • Core flow F C propagates along the core flowpath through compressor section 16, combustor 18 and turbine section 20, and bypass flow F B propagates along the bypass flowpath through bypass duct 14.
  • LPC section 30 and HPC section 32 of compressor 16 are utilized to compress incoming air for combustor 18, where fuel is introduced, mixed with air and ignited to produce hot combustion gas.
  • fan 12 also provides some degree of compression (or pre-compression) to core flow F C , and LPC section 30 may be omitted.
  • an additional intermediate spool is included, for example in a three-spool turboprop or turbofan configuration.
  • Turbine vanes 34 turn and accelerate the flow, and turbine blades 36 generate lift for conversion to rotational energy via HPT shaft 50, driving HPC section 32 of compressor 16 via HPT shaft 50.
  • Partially expanded combustion gas transitions from HPT section 38 to LPT section 40, driving LPC section 30 and fan 12 via LPT shaft 44.
  • thermodynamic efficiency of turbine engine 10 is tied to the overall pressure ratio, as defined between the delivery pressure at inlet 22 and the compressed air pressure entering combustor 18 from compressor section 16.
  • a higher pressure ratio offers increased efficiency and improved performance, including greater specific thrust.
  • High pressure ratios also result in increased peak gas path temperatures, higher core pressure and greater flow rates, increasing thermal and mechanical stress on engine components.
  • FIG. 2 is a cross section along line 2 - 2 of FIG. 1 of a casing 48 which has a rotor shaft 50 inside. Vanes 26 are attached to casing 48 and the gas path 52 is shown as the space between vanes 26. Coating 60, corresponding to the coating of this invention, is on rotor shaft 50 such that the clearance C between coating 60 and vane tips 26T of vanes 26 has the proper tolerance for operation of the engine, e.g., to serve as a seal to prevent leakage of air (thus reducing efficiency), while not interfering with relative movement of the vanes and rotor shaft.
  • clearance C is expanded for purposes of illustration.
  • clearance C may be, for example, in a range of about 0.025 inches to 0.055 inches (0.64-1.40 mm) when the engine is cold and 0.000 to 0.035 inches (0.00-0.89 mm) during engine operation, depending on the specific operating conditions and previous rub events that may have occurred.
  • FIG. 3 shows the cross section along line 3-3 of FIG. 2 , with casing 48 and vane 26.
  • Coating 60 is attached to rotor shaft 50, with a clearance C between coating 60 and vane tip 26T of vane 26 that varies with operating conditions, as described herein.
  • FIG. 3 shows an embodiment comprising bi-layer coating 60 in which includes metallic bond coat 62 and abradable layer 66.
  • Metallic bond coat 62 is applied to rotor shaft 50.
  • Abradable layer 66 is deposited on top of bond coat 62 and is the layer that first encounters vane tip 26T.
  • Bond coat 62 is thin, up to 10 mils (254 microns), more specifically ranging from about 3 mils to about 7 mils (about 76 to about 178 microns).
  • Abradable coating 66 is about the same thickness as bond coat 62, again ranging from about 3 mils to about 7 mils (about 76 to about 178 microns).
  • Bond coat 62 may be formed of MCrAlY, the metal (M) can be nickel, iron, or cobalt, or combinations thereof and the alloying elements are chromium (Cr), aluminum (Al) and yttrium (Y).
  • bond coat 62 may be 15-40% Cr 6-15% Al, 0.61 to 1.0%. Y and the balance is cobalt, nickel or iron and combinations thereof. It is applied in a conventional air plasma spray process.
  • Top abrasive layer 66 thickness may be relatively thin for smaller engine applications at about the same thickness as the bond coat layer 62, ranging from about 3 mils to about 7 mils (about 76 to about 178 microns) or it may be about 100 mils (2.5 mm) or more for larger engine applications. The required thickness depends on the size and characteristics of the specific engine application. For current aero-engine applications in the 10,000 to 35,000 pound thrust range (44-156 kN), the ideal abrasive layer thickness is about 5 to 15 mils (127-381 microns).
  • Abrasive layer 66 includes hexagonal boron nitride (hBN), a low strength filler, in an abrasive matrix.
  • the abrasive matrix may be any matrix used in aero-engine applications. Two specific matrix materials are ceramic matrixes and metal matrixes. The term "low strength filler" means that the filler material is of lower strength than the matrix material.
  • the ceramic matrix may be yttria stabilized zirconia or gadolinia-zirconate that is produced by thermal spray of ceramic particles.
  • the amount of hBN ranges from about 5 % to about 80 %, based on the volume of the coating, with the lowest concentration at the junction with bond coat 62.
  • the metal matrix may be selected from any suitable type of metal for an intended application.
  • the metal matrix may be selected from nickel, copper, molybdenum, aluminum or other metals.
  • the metal matrix may also be an alloy, such as a nickel alloy, such as those disclosed in commonly owned US Patent Nos. 5,536,022 and 5,780,116 .
  • Other metal matrix materials are also within the scope of this invention.
  • the amount of hBN as the low strength filler in abrasive layer 66 increases from the point of contact with bond coat layer 62 to the outer surface of abrasive layer 66.
  • the cohesive strength of abrasive layer 66 will range from about 2000 psi (14 MPa) at the boundary with bond coat layer 66 to about 200 psi to 300 psi (1.4-2.1 MPa) at the surface of abrasive layer 66. Because the amount of hBN increases and the cohesive strength decreases, any rubbing or other stress on abrasive layer 66 will cause abrasion of the layer at the surface. Any potential failure or wear will take place at the surface so that large quantities of spalling do not take place.
  • hBN functions as a low strength filler in abrasive layer 66.
  • Top abrasive layer 66 is applied with a Sulzer Metco 3MB air plasma spray (APS) torch setup that includes a G nozzle.
  • the torch to part distance is 4.25 inches (108 mm).
  • the part is set on a turntable and rotated to achieve a surface speed of 120 feet per minute (0.61 m/s) with an axial motion per revolution of the part of 0.2 inches (5 mm).
  • the amount of hBN is increased by changing the feed rates so that a higher concentration of hBN is achieved.
  • the feed rate for aluminum oxide powder is 60g/minute and is uniformly ramped down to 15 g/minute during coating buildup.
  • the feed rate for hBN is initially 5g/minute and ramped up to 25g/minute at the completion of coating. Because the cohesive strength of abrasive layer 66 has a gradient axially inward to a maximum at bond coat layer 62, wear and failure remains at the surface. What is also achieved is significantly improved clearance control because the abrasive layer 66 and the vane tips 26T both incur some shared shear, so that both abrade and a better seal is achieved.
  • Optional ceramic layer 64 may be any of the zirconia based ceramics such as are described in commonly U.S. Patent Nos. 4,861,618 , 5,879,573 , 6,102,656 and 6,358,002 .
  • Zirconia stabilized with 6-8 wt. % yttria is one example of such a ceramic layer 64.
  • Other examples are zirconia stabilized with ceria, magnesia, calcia, mullite and mixtures thereof.
  • Optional thermally insulating ceramic layer 64 thickness may range from about 7 mils to about 12 mils (about 178 to about 305 microns).
  • abrasive coating 66 functions to remove material by low temperature abrasion minimizing or eliminating thermal burn through of the rotor in high interaction rate events.
  • the cohesive strength of abrasive layer 66 again is strongest at the junction of the layers and weakest at its surface, as set forth above.
  • a metallic matrix material may be used.
  • the top layer of the coating it may be more conventional to describe the top layer of the coating as abradable as opposed to abrasive, however this is a matter of semantics.
  • the metallic matrix coating has a wear ratio with the airfoil tips that is caused by sliding contact wear.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Abreibende Beschichtung (60) für eine Rotorwelle, wobei die abreibende Beschichtung Folgendes umfasst:
    eine Metallhaftvermittlerschicht (62) auf der Rotorwelle (50);
    eine abreibende Schicht (66) über der Haftschicht zum Kontakt mit Leitschaufeln (26) während des Betriebs der Rotorwelle, wobei die abreibende Schicht eine Matrix umfasst, die ein Füllmaterial enthält, das von einer geringeren Festigkeit als die Matrix ist, wobei das Füllmittel radial nach außen von der Haftschicht zur Außenfläche der abreibenden Schicht eine erhöhte Konzentration aufweist;
    wobei die abreibende Schicht (66) hexagonales Bornitrid (hBN) als das Füllmittel mit geringer Festigkeit in einer Menge umfasst, die von 5 % bis 80 % reicht, basierend auf dem Volumen der Beschichtung, wobei die abreibende Schicht (66) eine erhöhte Konzentration von hBN radial nach außen von der Haftschicht zur Außenfläche der abreibenden Schicht aufweist; und
    wobei die Matrix Yttrium-stabilisiertes Zirconiumdioxid oder Gadolinium-Zirconat beinhaltet, oder
    wobei die Matrix mindestens ein Metall beinhaltet, das aus der Gruppe ausgewählt ist, die aus Nickel, Kupfer, Molybdän, Aluminium und Legierungen davon besteht.
  2. Abreibende Beschichtung nach Anspruch 1, wobei die Dicke der Metallhaftvermittlerschicht (62) von 3 Millizoll bis 7 Millizoll (76 bis 178 Mikrometer) reicht.
  3. Abreibende Beschichtung nach Anspruch 1 oder 2, wobei die Metallhaftvermittlerschicht (62) aus mindestens einem aus MCrAl, MCrAlY und einem feuerfesten modifizierten MCrAlY gebildet ist, wobei M Nickel, Eisen, Kobalt oder Mischungen davon ist.
  4. Abreibende Beschichtung nach Anspruch 3, wobei die Metallhaftvermittlerschicht (62) aus MCrAlY gebildet ist, wobei M Nickel oder Kobalt ist, und wobei die Legierungsbestandteile Chrom (Cr), Aluminium (Al) und Yttrium (Y) sind.
  5. Abreibende Beschichtung nach einem der vorstehenden Ansprüche, wobei die abreibende Schicht (66) eine Dicke von 3 Millizoll bis 7 Millizoll (76 bis 178 Mikrometer) aufweist.
  6. Abreibende Beschichtung nach einem der vorstehenden Ansprüche, wobei die abreibende Schicht (66) eine Kohäsionsfestigkeit am Punkt der Berührung mit dem Metallhaftvermittler von 2.000 psi (14 MPa) und eine Kohäsionsfestigkeit an ihrer Oberfläche von 200 psi (1,4 MPa) aufweist.
  7. Abreibende Beschichtung nach einem der vorstehenden Ansprüche, die ferner eine keramische Schicht (64) zwischen der Haftvermittlerschicht und der abreibenden Schicht umfasst.
  8. Abreibende Beschichtung nach Anspruch 7, wobei die keramische Schicht (64) eine Dicke im Bereich von 7 Millizoll bis 12 Millizoll (178 bis 305 Mikrometer) aufweist.
  9. Verdichter (16) für ein Gasturbinentriebwerk, umfassend:
    einen Rotor, der eine Vielzahl von axial beabstandeten Stufen von Verdichterschaufeln (28) aufweist, die daran befestigt sind und sich von einer Rotorwelle (50) nach außen erstrecken;
    eine Vielzahl von axial beabstandeten freitragenden Leitschaufeln (26), die sich nach innen in Richtung der Rotorwelle zum Kontakt mit einem Abschnitt der Rotorwelle erstrecken; und
    eine abreibende Beschichtung (60) nach einem der vorstehenden Ansprüche auf dem Abschnitt der Rotorwelle, um abreibbare Luftdichtungen mit den freitragenden Laufschaufeln zu bilden.
EP12173070.9A 2011-06-29 2012-06-21 Splitterbeständige abreibbare turbinenluftdichtung Active EP2540868B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/171,569 US8876470B2 (en) 2011-06-29 2011-06-29 Spall resistant abradable turbine air seal

Publications (2)

Publication Number Publication Date
EP2540868A1 EP2540868A1 (de) 2013-01-02
EP2540868B1 true EP2540868B1 (de) 2019-08-21

Family

ID=46458187

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12173070.9A Active EP2540868B1 (de) 2011-06-29 2012-06-21 Splitterbeständige abreibbare turbinenluftdichtung

Country Status (2)

Country Link
US (1) US8876470B2 (de)
EP (1) EP2540868B1 (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9145787B2 (en) * 2011-08-17 2015-09-29 General Electric Company Rotatable component, coating and method of coating the rotatable component of an engine
US20160032756A1 (en) * 2012-01-31 2016-02-04 United Technologies Corporation Low noise turbine for geared turbofan engine
WO2015112219A2 (en) * 2013-12-10 2015-07-30 United Technologies Corporation Fusible bond for gas turbine engine coating system
US10054059B2 (en) * 2014-09-15 2018-08-21 United Technologies Corporation Nacelle and compressor inlet arrangements
US11268183B2 (en) * 2015-05-06 2022-03-08 Raytheon Technologies Corporation Method of forming an abrasive coating on a fan blade tip
US10669878B2 (en) 2016-03-23 2020-06-02 Raytheon Technologies Corporation Outer airseal abradable rub strip
US10267174B2 (en) 2016-04-28 2019-04-23 United Technologies Corporation Outer airseal abradable rub strip

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1229252A2 (de) * 2001-02-05 2002-08-07 Solar Turbines Incorporated Abreibbare Beschichtung und Produktionsverfahren
US20040142196A1 (en) * 2003-01-17 2004-07-22 Karel Hajmrle Thermal spray composition and method of deposition for abradable seals
US20100284797A1 (en) * 2009-05-06 2010-11-11 General Electric Company Abradable seals
EP2481890A2 (de) * 2011-01-26 2012-08-01 United Technologies Corporation Dichtung in einem Gasturbinenbauteil mit einer Beschichtung mit zu einer Interaktionsrate proportionalen Abreibbarkeit

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3545944A (en) 1965-03-10 1970-12-08 United Aircraft Corp Composite metal article having an intermediate bonding layer of nickel aluminide
US4861618A (en) 1986-10-30 1989-08-29 United Technologies Corporation Thermal barrier coating system
US5536022A (en) * 1990-08-24 1996-07-16 United Technologies Corporation Plasma sprayed abradable seals for gas turbine engines
US6102656A (en) * 1995-09-26 2000-08-15 United Technologies Corporation Segmented abradable ceramic coating
US5879573A (en) 1997-08-12 1999-03-09 Vlsi Technology, Inc. Method for optimizing a gap for plasma processing
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
US6004362A (en) * 1998-02-02 1999-12-21 Lockheed Martin Energy Systems Method for forming an abrasive surface on a tool
SG72959A1 (en) 1998-06-18 2000-05-23 United Technologies Corp Article having durable ceramic coating with localized abradable portion
AU2001288459A1 (en) 2000-08-29 2002-03-13 Andrew W. Suman Abradable dry powder coatings, methods for making and coating, and coated articles therefrom
JP2002256808A (ja) * 2001-02-28 2002-09-11 Mitsubishi Heavy Ind Ltd 燃焼エンジン、ガスタービン及び研磨層
WO2002097160A1 (fr) 2001-05-31 2002-12-05 Mitsubishi Heavy Industries, Ltd. Procede et materiau de formage de revetement, et feuille de formage de revetement abrasif
EP1275748A3 (de) 2001-07-13 2004-01-07 ALSTOM (Switzerland) Ltd Hochtemperaturbeständiger Schutzüberzug mit eingebetteten lokalen Erhebungen sowie Verfahren zur Herstellung des Schutzüberzuges
US6706319B2 (en) 2001-12-05 2004-03-16 Siemens Westinghouse Power Corporation Mixed powder deposition of components for wear, erosion and abrasion resistant applications
US20060246275A1 (en) 2003-02-07 2006-11-02 Timothy Dumm Fiber and sheet equipment wear surfaces of extended resistance and methods for their manufacture
GB0400752D0 (en) * 2004-01-13 2004-02-18 Rolls Royce Plc Cantilevered stator stage
US20060093736A1 (en) * 2004-10-29 2006-05-04 Derek Raybould Aluminum articles with wear-resistant coatings and methods for applying the coatings onto the articles
US20080274336A1 (en) 2006-12-01 2008-11-06 Siemens Power Generation, Inc. High temperature insulation with enhanced abradability
US7998604B2 (en) 2007-11-28 2011-08-16 United Technologies Corporation Article having composite layer
US8008954B2 (en) * 2008-10-03 2011-08-30 Micron Technology, Inc. Multi-phase signal generator and method
US20120099971A1 (en) 2010-10-25 2012-04-26 United Technologies Corporation Self dressing, mildly abrasive coating for clearance control
US8790078B2 (en) 2010-10-25 2014-07-29 United Technologies Corporation Abrasive rotor shaft ceramic coating

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1229252A2 (de) * 2001-02-05 2002-08-07 Solar Turbines Incorporated Abreibbare Beschichtung und Produktionsverfahren
US20040142196A1 (en) * 2003-01-17 2004-07-22 Karel Hajmrle Thermal spray composition and method of deposition for abradable seals
US20100284797A1 (en) * 2009-05-06 2010-11-11 General Electric Company Abradable seals
EP2481890A2 (de) * 2011-01-26 2012-08-01 United Technologies Corporation Dichtung in einem Gasturbinenbauteil mit einer Beschichtung mit zu einer Interaktionsrate proportionalen Abreibbarkeit

Also Published As

Publication number Publication date
EP2540868A1 (de) 2013-01-02
US20130004301A1 (en) 2013-01-03
US8876470B2 (en) 2014-11-04

Similar Documents

Publication Publication Date Title
EP2481890A2 (de) Dichtung in einem Gasturbinenbauteil mit einer Beschichtung mit zu einer Interaktionsrate proportionalen Abreibbarkeit
EP2444593B1 (de) Brüchige abrasive Rotorwellenkeramikbeschichtung
US8770926B2 (en) Rough dense ceramic sealing surface in turbomachines
EP2540868B1 (de) Splitterbeständige abreibbare turbinenluftdichtung
EP2444513B1 (de) Abrasive Rotorwellenkeramikbeschichtung
EP3440318B1 (de) Dichtungsgeometrien für reduzierte leckage in gasturbinen und verfahren zur formung
US20240026120A1 (en) Wear resistant coating, method of manufacture thereof and articles comprising the same
EP3020931B1 (de) Abrasive rotorbeschichtung mit abriebskraftbegrenzungsmerkmalen
EP2444516A1 (de) Thermisches Aufspritzbeschichtungsverfahren für Verdichterwellen
EP2428593B1 (de) Abreibbare Beschichtung mit Sicherheitssicherung
EP3055445B1 (de) Aluminiumlegierungsbeschichtung mit seltenen erden und übergangsmetall-korrosionsinhibitoren
EP2444524A1 (de) Selbstabrichtende, leicht abrasive Beschichtung zur Spielsteuerung
EP3061850A1 (de) Hartphasenlose metallbeschichtung für verdichterschaufelspitze
US20130333392A1 (en) Turbine compressor blade tip resistant to metal transfer
EP2455589B1 (de) Aus thermischem Aufspritzen und Nachbehandlung hergestellte abrasive Schneidvorrichtung
EP2453110A1 (de) Verfahren zur Gestaltung einer Dichtung in einem Gasturbinentriebwerk, zugehörige Kombination eines Schaufelprofils und eine Dichtung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20130701

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20170315

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 602012063082

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: C23C0028000000

Ipc: F01D0005280000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/28 20060101AFI20190121BHEP

Ipc: F01D 11/12 20060101ALI20190121BHEP

INTG Intention to grant announced

Effective date: 20190226

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012063082

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1169983

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190915

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191223

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191121

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191121

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191122

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191221

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1169983

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200224

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012063082

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG2D Information on lapse in contracting state deleted

Ref country code: IS

26N No opposition filed

Effective date: 20200603

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200621

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200621

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190821

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602012063082

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240521

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240521

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240521

Year of fee payment: 13